Abstract

A simple method has been developed to determine the13; optimum flap deflection schedule and minimum drag envelope13; for given wing and flap geometries. The method is mainly13; based on linear theory and the optimum quot;solutionquot; is.13; determined by minirnising the lift dependent drag of the wing.The method can also be used in an inverse senso for the design of the gepmetry of plain flaps at leading and13; trailing edges.